SECTION 5 CESSNA
PERFORMANCE MODEL
2088 (675 SHP)
SAMPLE PROBLEM
(Continued)
CRUISE
The cruising altitude should be selected based on a consideration of
trip length, winds aloft, and the airplane's performance. A cruising
altitude and the expected wind
enroute have been given for this sample
problem. However, the power setting selection for cruise must be
determined based on several considerations. These include the cruise
performance characteristics presented in Figure 5-17, the Fuel and
Time Required charts presented in Figure 5-18 and 5-19, the Range
Profile chart presented in Figure 5-20, and the Endurance Profile chart
presented in figure 5-21.
The Range Profile chart, Figure 5-20, shows range at maximum cruise
power and also at maximum range power. For this sample problem,
maximum cruise power and 1900 RPM will be used.
The Cruise Performance chart for 12,000 feet pressure altitude is
entered using
10°C
temperature. These values most nearly correspond
to the planned altitude and expected temperature conditions. The
torque setting for maximum cruise power is 1280 Ft-Lbs torque at 1900
RPM which results in the following:
True Airspeed: 158 Knots
Cruise Fuel Flow: 306 PPH
FUEL REQUIRED
The total fuel requirement for the flight may be estimated using the
performance information in Figures 5-16, 5-17 and 5-22 or in Figures
5-
18 and 5-19. The longer detailed method will be used for this sample
problem, but the use of Figures 5-18 and 5-19 will provide the desired
information for most flight planning purposes.
(Continued Next Page)
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Revision
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